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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.04 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe180-il-1000000-n5.txt
Download as CSV file: xf-goe180-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.4681   0.16367   0.16187  -0.0026   1.0000   0.0041
 -13.750  -0.4578   0.15599   0.15420  -0.0055   1.0000   0.0042
 -10.250  -0.6815   0.02293   0.02007  -0.0871   0.9951   0.0090
 -10.000  -0.6537   0.01995   0.01676  -0.0895   0.9925   0.0096
  -9.750  -0.6232   0.01799   0.01453  -0.0915   0.9893   0.0103
  -9.500  -0.5910   0.01663   0.01295  -0.0933   0.9869   0.0109
  -9.250  -0.5604   0.01631   0.01263  -0.0940   0.9829   0.0116
  -8.750  -0.4990   0.01550   0.01173  -0.0956   0.9703   0.0130
  -8.500  -0.4668   0.01442   0.01043  -0.0970   0.9612   0.0138
  -8.250  -0.4310   0.01412   0.01008  -0.0988   0.9504   0.0144
  -8.000  -0.3953   0.01434   0.01033  -0.1003   0.9396   0.0148
  -7.750  -0.3621   0.01447   0.01044  -0.1013   0.9261   0.0153
  -7.500  -0.3328   0.01437   0.01026  -0.1015   0.9121   0.0159
  -7.250  -0.3056   0.01393   0.00966  -0.1015   0.9000   0.0166
  -7.000  -0.2789   0.01334   0.00889  -0.1014   0.8900   0.0173
  -6.750  -0.2517   0.01301   0.00841  -0.1012   0.8807   0.0178
  -6.500  -0.2248   0.01256   0.00784  -0.1011   0.8718   0.0182
  -6.250  -0.1975   0.01237   0.00759  -0.1010   0.8620   0.0186
  -6.000  -0.1702   0.01224   0.00740  -0.1008   0.8508   0.0190
  -5.750  -0.1428   0.01213   0.00723  -0.1007   0.8382   0.0194
  -5.500  -0.1156   0.01197   0.00698  -0.1005   0.8240   0.0199
  -5.250  -0.0886   0.01165   0.00654  -0.1003   0.8076   0.0204
  -5.000  -0.0619   0.01141   0.00615  -0.1000   0.7871   0.0210
  -4.750  -0.0352   0.01117   0.00575  -0.0996   0.7617   0.0216
  -4.500  -0.0088   0.01093   0.00533  -0.0993   0.7325   0.0220
  -4.250   0.0175   0.01078   0.00499  -0.0989   0.7000   0.0224
  -4.000   0.0439   0.01074   0.00476  -0.0985   0.6649   0.0227
  -3.750   0.0703   0.01070   0.00454  -0.0982   0.6267   0.0229
  -3.500   0.0970   0.01060   0.00427  -0.0979   0.5956   0.0230
  -3.250   0.1236   0.01004   0.00354  -0.0977   0.5722   0.0234
  -3.000   0.1507   0.00973   0.00312  -0.0975   0.5535   0.0238
  -2.750   0.1781   0.00951   0.00281  -0.0974   0.5376   0.0242
  -2.500   0.2058   0.00934   0.00257  -0.0973   0.5261   0.0245
  -2.250   0.2335   0.00922   0.00238  -0.0973   0.5145   0.0250
  -2.000   0.2613   0.00911   0.00223  -0.0972   0.5036   0.0255
  -1.750   0.2892   0.00900   0.00206  -0.0971   0.4948   0.0260
  -1.500   0.3171   0.00891   0.00192  -0.0971   0.4864   0.0265
  -1.250   0.3451   0.00883   0.00180  -0.0970   0.4792   0.0270
  -1.000   0.3731   0.00877   0.00169  -0.0970   0.4716   0.0275
  -0.750   0.4011   0.00872   0.00161  -0.0969   0.4636   0.0280
  -0.500   0.4288   0.00871   0.00154  -0.0968   0.4526   0.0284
  -0.250   0.4568   0.00868   0.00148  -0.0968   0.4443   0.0288
   0.000   0.4847   0.00868   0.00144  -0.0967   0.4383   0.0291
   0.250   0.5128   0.00865   0.00141  -0.0967   0.4332   0.0294
   0.500   0.5407   0.00867   0.00139  -0.0967   0.4258   0.0296
   0.750   0.5686   0.00867   0.00136  -0.0966   0.4177   0.0309
   1.000   0.5964   0.00869   0.00135  -0.0966   0.4102   0.0332
   1.250   0.6244   0.00870   0.00136  -0.0965   0.4051   0.0364
   1.500   0.6522   0.00865   0.00140  -0.0965   0.3983   0.0761
   1.750   0.6799   0.00866   0.00145  -0.0965   0.3910   0.1010
   2.000   0.7077   0.00858   0.00152  -0.0965   0.3829   0.1723
   2.250   0.7352   0.00849   0.00161  -0.0966   0.3740   0.2692
   2.750   0.7851   0.00719   0.00190  -0.0957   0.3488   1.0000
   3.000   0.8121   0.00737   0.00199  -0.0956   0.3299   1.0000
   3.250   0.8381   0.00765   0.00213  -0.0953   0.2999   1.0000
   3.500   0.8635   0.00802   0.00232  -0.0949   0.2664   1.0000
   4.000   0.9159   0.00854   0.00267  -0.0944   0.2338   1.0000
   4.250   0.9426   0.00874   0.00282  -0.0942   0.2253   1.0000
   4.500   0.9693   0.00893   0.00298  -0.0940   0.2184   1.0000
   4.750   0.9961   0.00910   0.00314  -0.0939   0.2127   1.0000
   5.000   1.0230   0.00927   0.00330  -0.0937   0.2079   1.0000
   5.250   1.0495   0.00946   0.00348  -0.0935   0.2027   1.0000
   5.500   1.0762   0.00964   0.00365  -0.0933   0.1983   1.0000
   5.750   1.1025   0.00984   0.00384  -0.0931   0.1901   1.0000
   6.000   1.1283   0.01009   0.00405  -0.0928   0.1784   1.0000
   6.250   1.1529   0.01048   0.00431  -0.0924   0.1552   1.0000
   6.500   1.1760   0.01102   0.00469  -0.0917   0.1269   1.0000
   6.750   1.2005   0.01139   0.00500  -0.0913   0.1159   1.0000
   7.000   1.2253   0.01171   0.00530  -0.0909   0.1085   1.0000
   7.250   1.2501   0.01202   0.00560  -0.0904   0.1019   1.0000
   7.500   1.2745   0.01236   0.00592  -0.0900   0.0924   1.0000
   8.000   1.3120   0.01417   0.00732  -0.0874   0.0268   1.0000
   8.250   1.3336   0.01474   0.00785  -0.0865   0.0181   1.0000
   8.500   1.3560   0.01520   0.00832  -0.0857   0.0144   1.0000
   8.750   1.3781   0.01568   0.00881  -0.0849   0.0122   1.0000
   9.000   1.4002   0.01613   0.00928  -0.0841   0.0108   1.0000
   9.250   1.4221   0.01658   0.00977  -0.0832   0.0099   1.0000
   9.500   1.4431   0.01708   0.01029  -0.0823   0.0090   1.0000
   9.750   1.4629   0.01767   0.01092  -0.0812   0.0081   1.0000
  10.000   1.4835   0.01815   0.01145  -0.0802   0.0077   1.0000
  10.250   1.5033   0.01866   0.01201  -0.0791   0.0072   1.0000
  10.500   1.5222   0.01922   0.01260  -0.0778   0.0067   1.0000
  10.750   1.5398   0.01984   0.01326  -0.0764   0.0062   1.0000
  11.000   1.5550   0.02059   0.01407  -0.0747   0.0058   1.0000
  11.250   1.5697   0.02122   0.01476  -0.0728   0.0056   1.0000
  11.500   1.5826   0.02188   0.01549  -0.0706   0.0054   1.0000
  11.750   1.5946   0.02262   0.01629  -0.0684   0.0052   1.0000
  12.000   1.6057   0.02342   0.01716  -0.0661   0.0050   1.0000
  12.250   1.6159   0.02431   0.01812  -0.0639   0.0048   1.0000
  12.500   1.6251   0.02530   0.01917  -0.0618   0.0046   1.0000
  12.750   1.6333   0.02641   0.02036  -0.0597   0.0045   1.0000
  13.000   1.6399   0.02770   0.02172  -0.0577   0.0043   1.0000
  13.250   1.6445   0.02923   0.02334  -0.0557   0.0042   1.0000
  13.500   1.6461   0.03112   0.02534  -0.0538   0.0040   1.0000
  13.750   1.6499   0.03293   0.02724  -0.0523   0.0039   1.0000
  14.000   1.6536   0.03486   0.02926  -0.0511   0.0039   1.0000
  14.250   1.6566   0.03698   0.03148  -0.0501   0.0038   1.0000
  14.500   1.6577   0.03941   0.03401  -0.0494   0.0037   1.0000
  14.750   1.6575   0.04215   0.03686  -0.0490   0.0036   1.0000
  15.000   1.6560   0.04520   0.04003  -0.0488   0.0035   1.0000
  15.250   1.6527   0.04861   0.04355  -0.0490   0.0035   1.0000
  15.500   1.6479   0.05235   0.04741  -0.0494   0.0034   1.0000
  15.750   1.6414   0.05647   0.05165  -0.0501   0.0034   1.0000
  16.000   1.6335   0.06085   0.05614  -0.0510   0.0033   1.0000
  16.250   1.6239   0.06557   0.06098  -0.0520   0.0033   1.0000
  16.500   1.6130   0.07058   0.06611  -0.0533   0.0032   1.0000
  16.750   1.6003   0.07587   0.07152  -0.0547   0.0032   1.0000
  17.000   1.5862   0.08148   0.07725  -0.0563   0.0032   1.0000
  17.250   1.5716   0.08729   0.08318  -0.0580   0.0031   1.0000
  17.500   1.5568   0.09319   0.08919  -0.0599   0.0031   1.0000
  17.750   1.5400   0.09958   0.09570  -0.0621   0.0031   1.0000
  18.000   1.5240   0.10597   0.10221  -0.0644   0.0031   1.0000
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